EP2932070A4 - Blindage thermique de chambre de combustion de moteur à turbine à gaz avec efficacité de refroidissement pelliculaire accrue - Google Patents

Blindage thermique de chambre de combustion de moteur à turbine à gaz avec efficacité de refroidissement pelliculaire accrue

Info

Publication number
EP2932070A4
EP2932070A4 EP13874386.9A EP13874386A EP2932070A4 EP 2932070 A4 EP2932070 A4 EP 2932070A4 EP 13874386 A EP13874386 A EP 13874386A EP 2932070 A4 EP2932070 A4 EP 2932070A4
Authority
EP
European Patent Office
Prior art keywords
gas turbine
turbine engine
heat shield
film cooling
cooling effectiveness
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP13874386.9A
Other languages
German (de)
English (en)
Other versions
EP2932070B1 (fr
EP2932070A2 (fr
Inventor
Nurhak Erbas-Sen
James B Hoke
Frank J Cunha
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of EP2932070A2 publication Critical patent/EP2932070A2/fr
Publication of EP2932070A4 publication Critical patent/EP2932070A4/fr
Application granted granted Critical
Publication of EP2932070B1 publication Critical patent/EP2932070B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00004—Preventing formation of deposits on surfaces of gas turbine components, e.g. coke deposits
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03042—Film cooled combustion chamber walls or domes
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP13874386.9A 2012-12-17 2013-12-16 Bouclier thermique de chambre de combustion de moteur à turbine à gaz avec efficacité de refroidissement pelliculaire accrue Active EP2932070B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/716,774 US20140216044A1 (en) 2012-12-17 2012-12-17 Gas turbine engine combustor heat shield with increased film cooling effectiveness
PCT/US2013/075388 WO2014123624A2 (fr) 2012-12-17 2013-12-16 Blindage thermique de chambre de combustion de moteur à turbine à gaz avec efficacité de refroidissement pelliculaire accrue

Publications (3)

Publication Number Publication Date
EP2932070A2 EP2932070A2 (fr) 2015-10-21
EP2932070A4 true EP2932070A4 (fr) 2015-12-23
EP2932070B1 EP2932070B1 (fr) 2019-05-08

Family

ID=51258081

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13874386.9A Active EP2932070B1 (fr) 2012-12-17 2013-12-16 Bouclier thermique de chambre de combustion de moteur à turbine à gaz avec efficacité de refroidissement pelliculaire accrue

Country Status (3)

Country Link
US (1) US20140216044A1 (fr)
EP (1) EP2932070B1 (fr)
WO (1) WO2014123624A2 (fr)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10260748B2 (en) * 2012-12-21 2019-04-16 United Technologies Corporation Gas turbine engine combustor with tailored temperature profile
WO2015023764A1 (fr) * 2013-08-16 2015-02-19 United Technologies Corporation Ensemble cloison de chambre de combustion de moteur de turbine à gaz
EP3039340B1 (fr) * 2013-08-30 2018-11-28 United Technologies Corporation Passages de dilution à tourbillonnement à section contractée pour chambre de combustion de moteur à turbine à gaz
US20160178199A1 (en) * 2014-12-17 2016-06-23 United Technologies Corporation Combustor dilution hole active heat transfer control apparatus and system
US10670267B2 (en) * 2015-08-14 2020-06-02 Raytheon Technologies Corporation Combustor hole arrangement for gas turbine engine
GB2545459B (en) * 2015-12-17 2020-05-06 Rolls Royce Plc A combustion chamber
JP6026028B1 (ja) * 2016-03-10 2016-11-16 三菱日立パワーシステムズ株式会社 燃焼器用パネル、燃焼器、燃焼装置、ガスタービン、及び燃焼器用パネルの冷却方法
US10830448B2 (en) * 2016-10-26 2020-11-10 Raytheon Technologies Corporation Combustor liner panel with a multiple of heat transfer augmentors for a gas turbine engine combustor
US10837640B2 (en) 2017-03-06 2020-11-17 General Electric Company Combustion section of a gas turbine engine
US20190277501A1 (en) * 2018-03-07 2019-09-12 United Technologies Corporation Slot arrangements for an impingement floatwall film cooling of a turbine engine
US11668463B2 (en) 2021-08-03 2023-06-06 Pratt & Whitney Canada Corp. Combustor with dilution holes

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4628694A (en) * 1983-12-19 1986-12-16 General Electric Company Fabricated liner article and method
US6170266B1 (en) * 1998-02-18 2001-01-09 Rolls-Royce Plc Combustion apparatus
US20100077764A1 (en) * 2008-10-01 2010-04-01 United Technologies Corporation Structures with adaptive cooling
US20100122537A1 (en) * 2008-11-20 2010-05-20 Honeywell International Inc. Combustors with inserts between dual wall liners

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2044912B (en) * 1979-03-22 1983-02-23 Rolls Royce Gas turbine combustion chamber
US4242871A (en) * 1979-09-18 1981-01-06 United Technologies Corporation Louver burner liner
GB2073396B (en) * 1980-03-29 1984-02-22 Rolls Royce Gas turbine combustion chambers
US4655044A (en) * 1983-12-21 1987-04-07 United Technologies Corporation Coated high temperature combustor liner
US5329773A (en) * 1989-08-31 1994-07-19 Alliedsignal Inc. Turbine combustor cooling system
CA2056592A1 (fr) * 1990-12-21 1992-06-22 Phillip D. Napoli Chemise de chambre de combustion a refroidissement par gaine d'air a trous multiples avec demarreur a gaine d'air rainuree
US7845174B2 (en) * 2007-04-19 2010-12-07 Pratt & Whitney Canada Corp. Combustor liner with improved heat shield retention
US8661826B2 (en) * 2008-07-17 2014-03-04 Rolls-Royce Plc Combustion apparatus
US8266914B2 (en) * 2008-10-22 2012-09-18 Pratt & Whitney Canada Corp. Heat shield sealing for gas turbine engine combustor
US8112216B2 (en) * 2009-01-07 2012-02-07 General Electric Company Late lean injection with adjustable air splits
US20100269513A1 (en) * 2009-04-23 2010-10-28 General Electric Company Thimble Fan for a Combustion System
US8397511B2 (en) * 2009-05-19 2013-03-19 General Electric Company System and method for cooling a wall of a gas turbine combustor
FR2953907B1 (fr) * 2009-12-11 2012-11-02 Snecma Chambre de combustion pour turbomachine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4628694A (en) * 1983-12-19 1986-12-16 General Electric Company Fabricated liner article and method
US6170266B1 (en) * 1998-02-18 2001-01-09 Rolls-Royce Plc Combustion apparatus
US20100077764A1 (en) * 2008-10-01 2010-04-01 United Technologies Corporation Structures with adaptive cooling
US20100122537A1 (en) * 2008-11-20 2010-05-20 Honeywell International Inc. Combustors with inserts between dual wall liners

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of WO2014123624A2 *

Also Published As

Publication number Publication date
WO2014123624A2 (fr) 2014-08-14
WO2014123624A3 (fr) 2014-10-23
EP2932070B1 (fr) 2019-05-08
EP2932070A2 (fr) 2015-10-21
US20140216044A1 (en) 2014-08-07

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